GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il) Reynolds number: 100,000 Max Cl/Cd: 56.33 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe140-il-100000-n5.txt Download as CSV file: xf-goe140-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 140 (MVA H.17) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2818 0.09572 0.09131 -0.0250 1.0000 0.0462
-7.250 -0.2825 0.09417 0.08986 -0.0288 1.0000 0.0468
-7.000 -0.2804 0.09217 0.08793 -0.0326 1.0000 0.0471
-6.750 -0.2774 0.08990 0.08571 -0.0354 1.0000 0.0472
-6.250 -0.2481 0.08035 0.07622 -0.0365 0.9895 0.0486
-5.750 -0.1775 0.07192 0.06759 -0.0536 0.9666 0.0572
-5.500 -0.1264 0.06752 0.06285 -0.0679 0.9523 0.0580
-5.250 -0.1119 0.06245 0.05790 -0.0671 0.9405 0.0589
-5.000 -0.0886 0.05889 0.05432 -0.0686 0.9270 0.0610
-4.750 -0.0363 0.05605 0.05103 -0.0793 0.9113 0.0684
-4.500 -0.0014 0.05216 0.04686 -0.0840 0.8962 0.0690
-4.250 0.0197 0.04808 0.04281 -0.0848 0.8804 0.0700
-4.000 0.0458 0.04509 0.03972 -0.0863 0.8636 0.0717
-3.750 0.0752 0.04256 0.03699 -0.0883 0.8463 0.0753
-3.500 0.1147 0.04034 0.03422 -0.0920 0.8292 0.0815
-3.250 0.1396 0.03761 0.03138 -0.0927 0.8110 0.0828
-2.750 0.2073 0.03191 0.02473 -0.0950 0.7757 0.0571
-2.500 0.2350 0.02992 0.02251 -0.0955 0.7572 0.0558
-2.250 0.2646 0.02820 0.02045 -0.0960 0.7385 0.0552
-2.000 0.2955 0.02687 0.01865 -0.0962 0.7192 0.0570
-1.750 0.3244 0.02548 0.01695 -0.0964 0.6998 0.0568
-1.500 0.3530 0.02421 0.01535 -0.0964 0.6805 0.0560
-1.000 0.4104 0.02213 0.01262 -0.0963 0.6430 0.0551
-0.750 0.4389 0.02128 0.01145 -0.0961 0.6244 0.0550
-0.500 0.4670 0.02055 0.01042 -0.0959 0.6064 0.0553
-0.250 0.4949 0.01991 0.00952 -0.0956 0.5893 0.0559
0.000 0.5226 0.01936 0.00872 -0.0952 0.5725 0.0568
0.250 0.5498 0.01896 0.00817 -0.0950 0.5563 0.0592
0.500 0.5767 0.01874 0.00788 -0.0948 0.5409 0.0635
0.750 0.6038 0.01843 0.00743 -0.0945 0.5262 0.0661
1.000 0.6304 0.01815 0.00703 -0.0941 0.5123 0.0680
1.250 0.6568 0.01787 0.00671 -0.0937 0.4992 0.0708
1.500 0.6836 0.01774 0.00649 -0.0934 0.4871 0.0757
1.750 0.7110 0.01767 0.00625 -0.0933 0.4758 0.0836
2.000 0.7385 0.01764 0.00611 -0.0932 0.4653 0.0997
2.250 0.7661 0.01761 0.00616 -0.0933 0.4550 0.1442
2.500 0.7873 0.01602 0.00618 -0.0919 0.4469 1.0000
2.750 0.8143 0.01631 0.00629 -0.0917 0.4377 1.0000
3.000 0.8411 0.01663 0.00644 -0.0915 0.4293 1.0000
3.250 0.8678 0.01694 0.00664 -0.0913 0.4212 1.0000
3.500 0.8945 0.01727 0.00688 -0.0912 0.4135 1.0000
3.750 0.9211 0.01761 0.00713 -0.0910 0.4064 1.0000
4.000 0.9477 0.01797 0.00744 -0.0909 0.4000 1.0000
4.250 0.9742 0.01832 0.00778 -0.0907 0.3936 1.0000
4.750 1.0270 0.01909 0.00853 -0.0904 0.3825 1.0000
5.000 1.0533 0.01949 0.00893 -0.0903 0.3773 1.0000
5.250 1.0794 0.01991 0.00931 -0.0901 0.3730 1.0000
5.500 1.1054 0.02032 0.00984 -0.0899 0.3670 1.0000
5.750 1.1311 0.02072 0.01027 -0.0897 0.3615 1.0000
6.000 1.1567 0.02114 0.01072 -0.0894 0.3565 1.0000
6.250 1.1814 0.02149 0.01117 -0.0891 0.3483 1.0000
6.500 1.2049 0.02175 0.01150 -0.0885 0.3370 1.0000
6.750 1.2280 0.02202 0.01180 -0.0879 0.3257 1.0000
7.000 1.2513 0.02234 0.01219 -0.0873 0.3155 1.0000
7.250 1.2734 0.02263 0.01254 -0.0866 0.3010 1.0000
7.500 1.2945 0.02298 0.01293 -0.0857 0.2843 1.0000
7.750 1.3169 0.02339 0.01347 -0.0851 0.2714 1.0000
8.000 1.3378 0.02387 0.01399 -0.0842 0.2546 1.0000
8.250 1.3584 0.02443 0.01461 -0.0834 0.2332 1.0000
8.500 1.3762 0.02523 0.01533 -0.0822 0.1987 1.0000
8.750 1.3787 0.02748 0.01695 -0.0797 0.1152 1.0000
9.000 1.3874 0.02924 0.01863 -0.0776 0.0886 1.0000
9.250 1.3796 0.03232 0.02132 -0.0741 0.0276 1.0000
9.500 1.3806 0.03424 0.02330 -0.0713 0.0239 1.0000
9.750 1.3815 0.03598 0.02517 -0.0685 0.0223 1.0000
10.000 1.3826 0.03787 0.02726 -0.0662 0.0216 1.0000
10.250 1.3816 0.04010 0.02970 -0.0643 0.0210 1.0000
10.500 1.3787 0.04276 0.03257 -0.0629 0.0206 1.0000
10.750 1.3736 0.04591 0.03594 -0.0621 0.0202 1.0000
11.000 1.3663 0.04965 0.03990 -0.0620 0.0200 1.0000
11.250 1.3568 0.05401 0.04447 -0.0625 0.0197 1.0000
11.500 1.3451 0.05900 0.04971 -0.0635 0.0195 1.0000
11.750 1.3320 0.06447 0.05539 -0.0650 0.0194 1.0000
12.000 1.3176 0.07031 0.06142 -0.0667 0.0193 1.0000
12.250 1.3031 0.07625 0.06754 -0.0684 0.0191 1.0000
12.500 1.2892 0.08214 0.07359 -0.0701 0.0190 1.0000
12.750 1.2759 0.08792 0.07953 -0.0717 0.0188 1.0000
13.000 1.2640 0.09351 0.08527 -0.0732 0.0187 1.0000
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Polar data table (+)
Polar graphs
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